[go: up one dir, main page]

WO2009019113A2 - Brûleur pour une chambre de combustion d'un turbogroupe - Google Patents

Brûleur pour une chambre de combustion d'un turbogroupe Download PDF

Info

Publication number
WO2009019113A2
WO2009019113A2 PCT/EP2008/059321 EP2008059321W WO2009019113A2 WO 2009019113 A2 WO2009019113 A2 WO 2009019113A2 EP 2008059321 W EP2008059321 W EP 2008059321W WO 2009019113 A2 WO2009019113 A2 WO 2009019113A2
Authority
WO
WIPO (PCT)
Prior art keywords
burner
lance
channel
outlet opening
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2008/059321
Other languages
German (de)
English (en)
Other versions
WO2009019113A3 (fr
Inventor
Jaan Hellat
Adnan Eroglu
Jan Cerny
Douglas Anthony Pennell
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=39865130&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=WO2009019113(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP08775142.6A priority Critical patent/EP2179222B2/fr
Publication of WO2009019113A2 publication Critical patent/WO2009019113A2/fr
Publication of WO2009019113A3 publication Critical patent/WO2009019113A3/fr
Priority to US12/694,506 priority patent/US8069671B2/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a burner for a combustion chamber of a turbo group, in particular in a power plant.
  • Such burners have a swirl generator, which encloses a burner interior on the input side and which has at least one air inlet tangential to a longitudinal central axis of the burner. Furthermore, such a burner comprises a mixer, which surrounds the burner interior on the output side and which has an outlet opening open to a combustion chamber of the combustion chamber. In addition, such a burner may be equipped with a lance for introducing pilot fuel into the combustion chamber. The lance is arranged coaxially to the longitudinal central axis of the burner and extends from a burner head, starting in the burner inside.
  • the invention deals with the problem of providing a burner of the type mentioned in an improved embodiment, which is characterized in particular by an increased stability of the combustion process in the combustion chamber.
  • the invention is based on the general idea to design the lance much longer, so that it can protrude deeper in the direction of the outlet opening into the burner interior.
  • the knowledge is used that a velocity profile is formed in the mixer for the mixture flow, which has significantly higher velocities in the center than in the edge region.
  • the targeted, in the direction of the outlet opening displaced positioning of the lance can also be achieved that a flame front, which arises during operation of the combustion chamber by the combustion reaction, at least partially into the burner interior protrudes. This is due to the reduced flow rate at the center of the velocity profile in the mixer. Due to the targeted positioning or extension of the lance thus the stationary flame front can partially extend within the burner interior. This is advantageous in several ways. On the one hand, the targeted introduction of fuel into the flame front can be improved with the help of the lance, since the distance between the free-standing lance end and the flame front is reduced.
  • the interaction between a plurality of burners of the combustion chamber is reduced via the combustion chamber, since the part of the flame front projecting into the respective burner interior is comparatively independent of the other burners with respect to the respective burner and thus stable.
  • the proposed construction thus makes it possible, in particular, to transfer results from test bench installations which only work with one burner to industrial installations in which the combustion chamber has a plurality of burners.
  • the lance has a plurality of concentrically arranged tubes, for example a central inner tube, which contains a central channel for liquid fuel and at least one axial outlet opening at the end of the lance.
  • a hollow-walled outer tube may be provided, which encloses the inner tube to form an inner annular channel and contains in its hollow wall at least one outer channel for gaseous fuel.
  • the inner ring channel ends axially open at the end of the lance and serves to guide air. Due to the proposed construction with concentric pipes, on the one hand, liquid fuel and, on the other hand, gaseous fuel can be supplied alternately or simultaneously via the lance. At the same time allows the air flow through the annular channel cooling the lance.
  • the air duct through the inner annular channel rinses the central channel or the at least one outer channel dispensable if only gaseous or only liquid fuel is supplied via the lance.
  • air inside the burner media separation between liquid fuel and gaseous fuel can be achieved at least to the flame front. This can be advantageous for realizing a stable combustion reaction.
  • FIG. 2 is a view as in Fig. 1, but in another embodiment,
  • FIGS. 1 and 2 are views as in FIGS. 1 and 2, but with the lance extended
  • Fig. 4 is a view as in FIGS. 1 and 2, but with a more detailed representation of the lance
  • Fig. 5 is a view as in Fig. 4, but in another embodiment of the lance.
  • a burner 1 comprises a swirl generator 2, a mixer 3 and a lance 4.
  • the burner 1 forms in the mounted state a component of a combustion chamber, not shown here, of a turbo group, which is arranged in particular in a power plant.
  • the swirl generator 2 encloses an input-side section of a burner interior 5 and has at least one air inlet 6, which extends tangentially with respect to a longitudinal central axis 7 of the burner 1.
  • the swirl generator 2 is configured conical.
  • the respective air inlet 6 forms a longitudinal slot along the cone sheath.
  • a plurality of such air inlets 6 are arranged distributed in the circumferential direction. As a result, the air can penetrate tangentially into the burner interior 5, whereby it is acted upon by a twist.
  • the swirl generator 2 also has a fuel inlet 8, via which gaseous fuel can be introduced into the burner interior 5.
  • this fuel inlet 8 consists of several, along the generatrix of the conical swirl generator 2 extending rows of individual inlet openings through which the fuel gas can enter the burner interior 5.
  • the fuel inlet 8 may be aligned tangentially to increase the swirl effect.
  • the fuel inlet 8 may generate some radial component to enhance mixing with the air.
  • the mixer 3 encloses an output-side section of the burner interior 5 and has an outlet opening 9, which is open to a combustion chamber 10 of the combustion chamber.
  • the mixer 3 comprises, for example, a tubular body 11, which is connected via a tubular transition piece 12 to the swirl generator 2 and which carries an outlet flange 13 with the outlet opening 9.
  • the burner 1 can be connected to the combustion chamber.
  • the mixer 3 is cylindrically shaped.
  • the lance 4 is used for introducing pilot fuel into the combustion chamber 10.
  • the lance 4 is arranged coaxially to the longitudinal central axis 7. Furthermore, at least in a pilot operation of the burner 1, the lance 4 extends into the burner interior 5 from a burner head 14, which essentially forms the tip of the conical swirl generator 2. The lance 4 thus starts from the burner head 14 and ends with a lance end 15 freestanding in the burner interior. 5
  • a part of a flame front 16 is also shown, which forms during operation of the combustion chamber by the combustion reaction taking place in the combustion chamber 10.
  • part of this flame front 16 projects into the burner interior 5, specifically into an end section of the burner interior 5, which is enclosed by an outlet-side end region of the mixer 3.
  • the flame front 16 remains within the section of the burner interior 5 enclosed by the outlet flange 13.
  • Such a course of the flame front 16, in which a part of the flame front 16 projects through the outlet opening 9 into the burner interior 5, is characterized by a particular embodiment and / or or arrangement of the lance 4 reached.
  • the lance 4 In pilot operation of the burner 1, the lance 4 extends with its free-standing end 15 comparatively far in the Burner interior 5 in, namely so far that a part of the flame front 16 extends into the burner interior 5 inside.
  • the lance 4 can protrude so deep into the burner interior 5 in the direction of the outlet opening 9, the lance 4 must be designed accordingly so that it has the necessary axial length for this purpose.
  • the lance 4 is positioned in the burner 1 so that its free-standing end 15 is located in a portion of the burner interior 5 enclosed by the mixer 3. In other words, the lance 4 extends into the mixer 3.
  • the lance 4 with its free-standing end 15 in the axial direction to about half of the mixer 3 or even beyond in the mixer 3 extend into it.
  • a distance 17 entered in FIG. 2, which the freestanding lance end 15 has from the outlet opening 9 is greater than 25% or less than 50% of a distance 18 that an outlet end 19 of the swirl generator 2 has from the outlet opening 9.
  • the distance 17 between outlet opening 9 and lance end 15 is preferably in a range of 25% to 50% of the distance 18 prevailing between outlet opening 9 and outlet-side end 19.
  • an inlet tube 20, which extends coaxially with the lance 4, can be arranged on the burner head 14.
  • This inlet tube 20 protrudes in the axial direction into a section of the burner interior 5 enclosed by the swirl generator 2.
  • This inlet pipe 20 may form an annular inlet channel 21 for liquid fuel.
  • the inlet channel 21 has at least one axially oriented outlet opening 22.
  • the liquid fuel can enter the burner interior 5 substantially in the axial direction, as indicated by arrows 48.
  • the burner 1 can thus be operated with fuel gas and / or with liquid fuel.
  • a plurality of such axial outlet openings 22 are arranged at the end of the inlet tube 20 ending in the burner interior 5.
  • the lance 4 may be arranged in the axial direction adjustable on the burner head 14.
  • the axial position of the free-standing lance end 15 within the burner interior 5 is adjustable.
  • this allows the position of the part of the flame front 16 projecting into the burner interior 5 to be adjusted.
  • the burner 1 can be adapted to operating parameters of the combustion chamber, which allows stabilization of the combustion process.
  • the lance 4 can thus be retracted more or less deep into the burner interior 5, depending on demand, or extend more or less far out of the burner interior 5.
  • Fig. 3 shows a situation in which the lance 4 is largely extended from the burner interior 5.
  • the lance end 15 expediently ends at the inside of the burner head 14 facing the burner interior 5.
  • the lance 4 is fully extended for a simplified illustration. It can be retracted according to an arrow 23 back into the burner interior 5.
  • the flame front 16 is arranged completely outside the burner interior 5 and is located downstream of the outlet opening 9 with respect to the flow direction of the burner 1.
  • a velocity profile 24 is shown in simplified form, which represents the distribution of the flow velocity along the cross section of the burner 1 within the mixer 3. Visible, the flow has a significant maximum in the absence of lance 4 in the center.
  • the flow velocity in the center of the cross section of the mixer 3 is inevitably reduced.
  • the speed is correspondingly increased outside the lance 4, ie in the edge region of the cross section, in order to ensure a constant volume flow.
  • the reduction of central flow velocity allows the flame front 16 to travel upstream. With appropriate positioning and configuration of the lance 4, the flame front 16 projects partially into the burner interior 5, as shown in FIG.
  • Figs. 4 and 5 the lance 4 is also shown cut.
  • the following detailed description of the lance 4 applies in particular to the embodiments of FIGS. 1 to 3.
  • the lance 4 has a plurality of concentrically arranged tubes, namely a central inner tube 25 and an outer tube 26.
  • the inner tube 25 includes a central channel 27 and has at least the free-standing lance end 15 axially oriented outlet opening 28.
  • the central channel 27 serves to supply liquid fuel to the at least one outlet opening 28.
  • the inner tube 25 includes a central channel 27 and has at least the free-standing lance end 15 axially oriented outlet opening 28.
  • the central channel 27 serves to supply liquid fuel to the at least one outlet opening 28.
  • the outer tube 26 is sized so that it surrounds the inner tube 25 to form an inner annular channel 30.
  • This inner annular channel 30 is axially open at the end of the lance 15 and thus opens into the burner interior 5.
  • the inner annular channel 30 serves to guide air, which can emerge from the inner annular channel 30 in the axial direction according to an arrow 31.
  • the outer tube 26 is configured hollow-walled, that is, the outer tube 26 has a hollow wall 33 with an inner wall 34 and a radially spaced outer wall 35.
  • the hollow wall 33 includes the outer tube
  • This at least one outer channel 36, 37 serves to supply gaseous fuel.
  • the outer channel 36, 37 may be configured as an annular channel, which is simply formed between the two walls 34, 35 of the wall 33. According to FIG. 4, this outer annular channel 36 or 37 can have at least one axially oriented outlet opening 38 on the lance end 15, as a result of which an essentially axially oriented injection of fuel gas can be achieved in accordance with an arrow 39.
  • an array of a plurality of radial outlet openings 41 may be provided in an in Fig. 5 marked with a brace lance end portion 40, which has the free-standing lance end 15, an array of a plurality of radial outlet openings 41 may be provided.
  • These radial outlet openings 41 are preferably formed in the outer wall 35 of the hollow wall 33 of the outer tube 26. As a result, a substantially radially oriented injection of the fuel gas into the burner interior 5 can be realized. The thus radially injected gaseous fuel is thereby deflected according to arrows 42 due to the prevailing axial flow in the burner interior in the axial direction.
  • a corresponding control can be provided which, for example, operates with a sleeve-shaped control element which lies in a first position in front of the radial outlet openings 41. while it locks in a second position, the at least one axial outlet opening 38.
  • a plurality of circumferentially distributed axial outlet openings 38 are arranged at the axial end of the outer tube 26.
  • At least a first outer channel 36 may be formed, which at the lance end 15 to the at least one axial outlet opening 38 leads.
  • at least one second outer channel 37 may be formed in the hollow wall 33, which leads to at least one of the radial outlet openings 41 formed in the lance end section 40.
  • FIG. 4 shows a section through the first outer channels 36
  • FIG. 5 shows a section through the second outer channels 37.
  • the first and second outer channels 36, 37 may be connected on the input side to various, independently operable supply devices or control devices. This makes it possible, the introduction of the gaseous fuel optionally only through the at least one axial outlet opening 38 or only through the at least one radial
  • Outlet opening 41 or 41 to introduce both through the at least one axial outlet opening 38 and through the at least one radial outlet opening 41.
  • the inner tube 25 projects axially beyond the outer tube 26. In this way, a certain separation of media during operation of the lance 4 for injecting the liquid fuel and for injecting the fuel gas can be achieved. This media separation can also be assisted by the injected air 31.
  • the inlet pipe 20 arranged at the burner head 14 is hollow-walled, so that it has a hollow wall 43 with an inner wall 44 and an outer wall 45.
  • the hollow-walled inlet tube 20 is here also dimensioned so that it encloses the lance 4 and the outer tube 26 to form an axially open annular channel 46. Through this annular channel 46 47 air can be injected into the burner interior according to an arrow. In this way, an effective cooling of the lance in the region of the burner head 14 can be achieved.
  • the inlet channel 21 corresponding to the introduction of the liquid fuel Arrows 48 is used, is formed in the hollow wall 43 and may also be configured in particular ring-shaped.
  • a wall 49 of the mixer 3 is provided with a film cooling 50.
  • a film cooling 50 is realized for example by means of a plurality of cooling holes 51 which pass through the corresponding wall 49 and can be flowed through by coolant, which applies to the side of the wall 49 facing the burner interior 5 and thereby generates a cooling film protecting the wall 49.
  • coolant is usually air.
  • the cooling holes 51 may be set in the main flow direction of the burner 1 as shown here to enhance the formation of a cooling film.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Abstract

L'invention concerne un brûleur (1) pour une chambre de combustion d'un turbogroupe, comprenant un générateur de torsion (2), un mélangeur (3) et une lance (4) destinée à déposer le combustible pilote dans une chambre de combustion (10). Pour stabiliser la combustion, la lance (4) est conçue et/ou disposée de façon à s'étendre au moins en mode pilote du brûleur (1) assez profondément à l'intérieur du brûleur (5) pour qu'un front de flamme (16) d'une réaction de combustion s'écoulant dans la chambre de combustion (10) s'étende au moins partiellement jusqu'à l'intérieur du brûleur (5).
PCT/EP2008/059321 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe Ceased WO2009019113A2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08775142.6A EP2179222B2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe
US12/694,506 US8069671B2 (en) 2007-08-07 2010-01-27 Burner fuel lance configuration and method of use

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007037289.4 2007-08-07
DE102007037289 2007-08-07

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/694,506 Continuation US8069671B2 (en) 2007-08-07 2010-01-27 Burner fuel lance configuration and method of use

Publications (2)

Publication Number Publication Date
WO2009019113A2 true WO2009019113A2 (fr) 2009-02-12
WO2009019113A3 WO2009019113A3 (fr) 2009-06-11

Family

ID=39865130

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/059321 Ceased WO2009019113A2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe

Country Status (3)

Country Link
US (1) US8069671B2 (fr)
EP (1) EP2179222B2 (fr)
WO (1) WO2009019113A2 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
US20120297777A1 (en) * 2009-11-07 2012-11-29 Alstom Technology Ltd Reheat burner injection system with fuel lances
US8490398B2 (en) 2009-11-07 2013-07-23 Alstom Technology Ltd. Premixed burner for a gas turbine combustor
US8572980B2 (en) 2009-11-07 2013-11-05 Alstom Technology Ltd Cooling scheme for an increased gas turbine efficiency
EP2685160A1 (fr) 2012-07-10 2014-01-15 Alstom Technology Ltd Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US8677756B2 (en) 2009-11-07 2014-03-25 Alstom Technology Ltd. Reheat burner injection system
EP3299720A1 (fr) 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
US8413446B2 (en) * 2008-12-10 2013-04-09 Caterpillar Inc. Fuel injector arrangement having porous premixing chamber
US20100175380A1 (en) * 2009-01-13 2010-07-15 General Electric Company Traversing fuel nozzles in cap-less combustor assembly
CN103975200B (zh) * 2011-12-05 2016-03-16 通用电气公司 多区域燃烧器
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
US9441543B2 (en) * 2012-11-20 2016-09-13 Niigata Power Systems Co., Ltd. Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion
US8943834B2 (en) * 2012-11-20 2015-02-03 Niigata Power Systems Co., Ltd. Pre-mixing injector with bladeless swirler
EP3133342A1 (fr) * 2015-08-20 2017-02-22 Siemens Aktiengesellschaft Brûleur à double carburant prémélangé avec un composant d'injection éfilé de carburant liquide principal
EP3523579B1 (fr) * 2016-10-10 2021-12-15 King Abdullah University Of Science And Technology Brûleurs et procédés pour conversion de méthane en oléfines, composés aromatiques et nanoparticules
US10907832B2 (en) 2018-06-08 2021-02-02 General Electric Company Pilot nozzle tips for extended lance of combustor burner
GB2585025A (en) * 2019-06-25 2020-12-30 Siemens Ag Combustor for a gas turbine
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures
WO2022079523A1 (fr) * 2020-10-14 2022-04-21 King Abdullah University Of Science And Technology Injecteur réglable de carburant pour commande de dynamique de flamme
CN113587087A (zh) * 2021-07-28 2021-11-02 西安西热锅炉环保工程有限公司 一种预混型富氢废气掺烧燃烧器
US11692711B2 (en) * 2021-08-13 2023-07-04 General Electric Company Pilot burner for combustor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur
DE10334228A1 (de) 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens
DE10345137A1 (de) 2003-09-29 2005-04-21 Alstom Technology Ltd Baden Verfahren zum Betrieb einer Brennstoffeinspritzvorrichtung sowie eine Brennstoffeinspritzvorrichtung zur Durchführung des Verfahrens
EP1526333A1 (fr) 2003-10-23 2005-04-27 United Technologies Corporation Injecteur de carburant pour turbines à gaz
DE102005015152A1 (de) 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
JP2713627B2 (ja) * 1989-03-20 1998-02-16 株式会社日立製作所 ガスタービン燃焼器、これを備えているガスタービン設備、及びこの燃焼方法
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE4446842B4 (de) * 1994-12-27 2006-08-10 Alstom Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner
DE19510744A1 (de) * 1995-03-24 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
DE19527453B4 (de) † 1995-07-27 2009-05-07 Alstom Vormischbrenner
DE19545310B4 (de) † 1995-12-05 2008-06-26 Alstom Vormischbrenner
DE19545309A1 (de) † 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
DE19547913A1 (de) † 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19640198A1 (de) † 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
US5735466A (en) * 1996-12-20 1998-04-07 United Technologies Corporation Two stream tangential entry nozzle
JP3448190B2 (ja) * 1997-08-29 2003-09-16 三菱重工業株式会社 ガスタービンの燃焼器
WO2001096785A1 (fr) † 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange
DE10050248A1 (de) † 2000-10-11 2002-04-18 Alstom Switzerland Ltd Brenner
DE10051221A1 (de) † 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE10104695B4 (de) † 2001-02-02 2014-11-20 Alstom Technology Ltd. Vormischbrenner für eine Gasturbine
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10205839B4 (de) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
US6786046B2 (en) * 2002-09-11 2004-09-07 Siemens Westinghouse Power Corporation Dual-mode nozzle assembly with passive tip cooling
US7284378B2 (en) * 2004-06-04 2007-10-23 General Electric Company Methods and apparatus for low emission gas turbine energy generation
EP1802915B1 (fr) * 2004-10-18 2016-11-30 General Electric Technology GmbH Bruleur pour turbine a gaz
EP1943464A1 (fr) † 2005-11-04 2008-07-16 ALSTOM Technology Ltd Lance à combustible
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur
DE10334228A1 (de) 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens
DE10345137A1 (de) 2003-09-29 2005-04-21 Alstom Technology Ltd Baden Verfahren zum Betrieb einer Brennstoffeinspritzvorrichtung sowie eine Brennstoffeinspritzvorrichtung zur Durchführung des Verfahrens
EP1526333A1 (fr) 2003-10-23 2005-04-27 United Technologies Corporation Injecteur de carburant pour turbines à gaz
DE102005015152A1 (de) 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
US8938968B2 (en) 2008-12-19 2015-01-27 Alstom Technology Ltd. Burner of a gas turbine
US20120297777A1 (en) * 2009-11-07 2012-11-29 Alstom Technology Ltd Reheat burner injection system with fuel lances
US8490398B2 (en) 2009-11-07 2013-07-23 Alstom Technology Ltd. Premixed burner for a gas turbine combustor
US8572980B2 (en) 2009-11-07 2013-11-05 Alstom Technology Ltd Cooling scheme for an increased gas turbine efficiency
US8677756B2 (en) 2009-11-07 2014-03-25 Alstom Technology Ltd. Reheat burner injection system
US8713943B2 (en) * 2009-11-07 2014-05-06 Alstom Technology Ltd Reheat burner injection system with fuel lances
EP2685160A1 (fr) 2012-07-10 2014-01-15 Alstom Technology Ltd Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US8950187B2 (en) 2012-07-10 2015-02-10 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
EP3299720A1 (fr) 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz

Also Published As

Publication number Publication date
WO2009019113A3 (fr) 2009-06-11
US20100146983A1 (en) 2010-06-17
EP2179222B2 (fr) 2021-12-01
EP2179222A2 (fr) 2010-04-28
EP2179222B1 (fr) 2014-10-22
US8069671B2 (en) 2011-12-06

Similar Documents

Publication Publication Date Title
EP2179222B1 (fr) Brûleur pour une chambre de combustion d'un turbogroupe
DE2131490C2 (de) Brenner-Mischdüse
EP3087323B1 (fr) Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur
EP2369231B1 (fr) Dispositif de mélange pour un brûleur à gaz
EP3559551B1 (fr) Dispositif de mélange et tête de brûleur pour un brûleur à émission de nox réduite
EP1802915B1 (fr) Bruleur pour turbine a gaz
EP1456583B1 (fr) Procédé d'injection d'un mélange air/carburant dans une chambre de combustion
EP0548396B1 (fr) Dispositif servant à mélanger deux composants gazeux et brûleur dans lequel ce dispositif est appliqué
DE2538512A1 (de) Brennkammer mit abgestuften vormischungsrohren
EP2116766A1 (fr) Lance à combustible
CH680467A5 (fr)
EP2232147B1 (fr) Brûleur et procédé pour réduire des oscillations de flammes autoinduites
DE112014004695T5 (de) Brennstoffeinspritzvorrichtung für eine Gasturbine
EP3198199A1 (fr) Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
EP1864056B1 (fr) Bruleur de premelange destine a une chambre de combustion de turbine a gaz
DE102009054669A1 (de) Brenner für eine Turbine
DE1198130B (de) Brenner fuer ringfoermige Brennkammern
EP0483554B1 (fr) Procédé pour la réduction au minimum des émissions de NOx dans une combustion
DE19654008A1 (de) Brenner
WO2009019114A2 (fr) Combustible pour une chambre de combustion d'un turbogroupe
DE19507088B4 (de) Vormischbrenner
DE855177C (de) Einrichtung fuer die kontinuierliche Verbrennung von Brennstoff in einem rasch fliessenden Luftstrom
DE19733768C2 (de) Brenngas-Einleitungsvorrichtung für einen Gas-Vormischbrenner
EP1943464A1 (fr) Lance à combustible
DE102017118166A1 (de) Brennerkopf, Brennersystem und Verwendung des Brennersystems

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08775142

Country of ref document: EP

Kind code of ref document: A2

WWE Wipo information: entry into national phase

Ref document number: 2008775142

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE